US5458304A — Disk spoiler system

Claim 1

Independent Claim 280 words

A drag-spoiling apparatus, in an aircraft having tail airfoil structures of near-symmetrical surfaces, and a pilot-command communicating means to a rudder actuating apparatus; an improvement comprising: a left-side barrier-line spoiler means, mounted within the aircraft's vertical stabilizer tail surfaces, and attached to the vertical stabilizer's structure and connected to a left-side barrier-line spoiler actuating means; and a right-side barrier-line spoiler means mounted within the aircraft's vertical stabilizer tail surfaces, and attached to the vertical stabilizer's structure and connected to a right-side barrier-line spoiler actuating means; and surface-pressure sensor means, located aft of the barrier line spoiler on each side of the vertical stabilizer (FIG. 4-4.1), and computer means, with trim algorithm means (FIG. 6) connected to the sensor means, and connected to electrical means connected to the spoiler actuation means; wherein spoiler means generate a controllable-height profile barrier-line such as can be generated by computer-defined, multiple, closely-parallel, eccentrically-rotated, powered disks; and wherein spoilers controllably pass through each airfoil side surface to disrupt laminar airflow of its airfoil side; and, wherein data from the surface pressure sensors, is communicated to the computer means (FIG. 1-9), and the computer provides powered instructions of a trim algorithm (FIG. 5) to compute and command the actuation of the spoilers; and, wherein the computer means receive electrical data representing pressure patterns and compares it with aircraft pressure patterns of minimum lift-induced drag; wherein electrical actuation means receive computer-level electric output and convert it to energy means suitable for actuation of spoilers into barrier profiles; whereby pressure sensors and computers sense and compare air pressure from opposite sides of the vertical tail surface, and computer-driven output actuates spoiler barrier profile movement to reduce unnecessary lift-induced drag.

Claim 2

Dependent Claim 280 words

A drag-spoiling apparatus, in an aircraft having tail airfoil structures of near-symmetrical surfaces, and a pilot-command communicating means to a rudder actuating apparatus; an improvement comprising: a left-side barrier-line spoiler means, mounted within the aircraft's vertical stabilizer tail surfaces, and attached to the vertical stabilizer's structure and connected to a left-side barrier-line spoiler actuating means; and a right-side barrier-line spoiler means mounted within the aircraft's vertical stabilizer tail surfaces, and attached to the vertical stabilizer's structure and connected to a right-side barrier-line spoiler actuating means; and surface-pressure sensor means, located aft of the barrier line spoiler on each side of the vertical stabilizer (FIG. 4-4.1), and computer means, with trim algorithm means (FIG. 6) connected to the sensor means, and connected to electrical means connected to the spoiler actuation means; wherein spoiler means generate a controllable-height profile barrier-line such as can be generated by computer-defined, multiple, closely-parallel, eccentrically-rotated, powered disks; and wherein spoilers controllably pass through each airfoil side surface to disrupt laminar airflow of its airfoil side; and, wherein data from the surface pressure sensors, is communicated to the computer means (FIG. 1-9), and the computer provides powered instructions of a trim algorithm (FIG. 5) to compute and command the actuation of the spoilers; and, wherein the computer means receive electrical data representing pressure patterns and compares it with aircraft pressure patterns of minimum lift-induced drag; wherein electrical actuation means receive computer-level electric output and convert it to energy means suitable for actuation of spoilers into barrier profiles; whereby pressure sensors and computers sense and compare air pressure from opposite sides of the vertical tail surface, and computer-driven output actuates spoiler barrier profile movement to reduce unnecessary lift-induced drag.

Claim 3

Dependent Claim 32 words

A drag-spoiling apparatus of claim 1, further comprising; multiple barrier lines of spoiler means; wherein multiple, parallel lines of spoilers (FIG. 4-6.3) are mounted on forward surfaces of tail airfoils (FIG. 4-4.1.)

Claim 4

Dependent Claim 119 words

A spoiler-driven drag-optimization method comprising: airfoil surface areas (FIG. 4-4.1), fitted with lines of spoiler devices (FIG. 4-6.1), with electrically controlled actuators and pressure sensors (FIG. 2-7) located aft (FIG. 4-7) of the spoilers; and an aircraft computer with drag-minimizing software algorithms, and with communicating means (FIG. 1-11) from sensors to spoiler actuators, and communication means to reveal index of exposed spoilers and reveal surface pressure on symmetrical tail surfaces, and related flight parameters; wherein a surface pressure feedback method determines surface spoiler commands; and wherein surface pressure on said airfoils is sensed and electrically reported to reveal sources of lift and drag under conditions of aircraft flight; and computer deduced drag-reducing trimming actions are communicated to said spoilers.

Claim 5

Dependent Claim 119 words

A spoiler-driven drag-optimization method comprising: airfoil surface areas (FIG. 4-4.1), fitted with lines of spoiler devices (FIG. 4-6.1), with electrically controlled actuators and pressure sensors (FIG. 2-7) located aft (FIG. 4-7) of the spoilers; and an aircraft computer with drag-minimizing software algorithms, and with communicating means (FIG. 1-11) from sensors to spoiler actuators, and communication means to reveal index of exposed spoilers and reveal surface pressure on symmetrical tail surfaces, and related flight parameters; wherein a surface pressure feedback method determines surface spoiler commands; and wherein surface pressure on said airfoils is sensed and electrically reported to reveal sources of lift and drag under conditions of aircraft flight; and computer deduced drag-reducing trimming actions are communicated to said spoilers.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1998-10-16	1999-04-17	1999-10-17	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	2002-10-16	2003-04-17	2003-10-17	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	2006-10-16	2007-04-17	2007-10-17	$7700.00	Window Closed / Lapsed

Disk spoiler system

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